Flight Path Segment Insertion Without Phase Reconstruction

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Solution Overview

Problem

Current low-altitude flight management systems do not allow for the separation of an existing low-altitude flight phase into two distinct phases while maintaining the original structure, requiring pilots to reconstruct the entire phase when inserting an intermediate section, which is time-consuming and loses the structure of the second part of the path.

Innovation Solution

A method and device that allow the insertion of an intermediate section into a low-altitude flight phase by redistributing parameters to allocate them to upstream, downstream, and intermediate sections, maintaining the original structure by calculating and inserting a speed and altitude profile between these sections, enabling a continuous revised flight phase with two upstream and downstream parts.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Loss of time

If the pilot modifies the path by selecting a new phase entry or exit waypoint, then the LLF phase can be shortened, but the second part of the LLF path is lost and must be integrally reconstructed

Engineering Contradiction:

Improvetime to modify flight phaseVSAvoidcomplexity of flight phase reconstruction

Core Design Contradiction:

Loss of timeVSDevice complexity

Solution Approach 1:

The patent segments the original LLF phase into multiple parts (first part, second part, and intermediate section) that can be independently managed and recombined. This allows the pilot to insert an intermediate section without losing the second part of the original path, as each segment can be preserved and reassembled in the revised flight phase.

Inventive Principle:

Principle #1Segmentation

2Adaptability or versatility

If the LLF function allows separation of an existing LLF phase into two separate phases, then an intermediate section can be inserted, but the system currently does not support this capability

Engineering Contradiction:

Improveflexibility of flight phase modificationVSAvoidcomplexity of flight management system

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The patent implements a dynamic flight phase management system that allows the LLF phase to be flexibly modified during flight. The system can separate an existing LLF phase into two separate phases, insert an intermediate section with specific parameters (altitude, speed, waypoints), and maintain the original structure of both parts, providing adaptability without requiring complete reconstruction.

Inventive Principle:

Principle #15Dynamics

3Reliability

If the pilot reconstructs a new LLF phase by re-inserting the same parameters, then the second part of the LLF path can be retrieved, but this process is time-consuming

Engineering Contradiction:

Improveintegrity of flight pathVSAvoidtime to reconstruct flight phase

Core Design Contradiction:

ReliabilityVSLoss of time

Solution Approach 1:

The patent applies preliminary action by automatically preserving and storing the parameters of both the first and second parts of the original LLF phase before any modification occurs. When an intermediate section needs to be inserted, the system retrieves these pre-preserved parameters and automatically reassembles the complete flight phase, eliminating the need for time-consuming manual reconstruction and ensuring parameter integrity.

Inventive Principle:

Principle #10Preliminary action

Data Source

PatentUS9286806B2Method and device for revising a low-altitude flight phase of a flight path of an aircraft

Publication Date: 2016.03.15 AIRBUS OPERATIONS (SAS)

AI summary

A device for revising a low-altitude flight phase of a flight path of an aircraft includes an input unit configured to allow an operator to input parameters to define an intermediate flight section (Si) which has to be inserted into a low-altitude flight phase, and a processing unit configured to calculate a profile relating to the intermediate flight section (Si) using input parameters, and to automatically insert this profile into the flight phase between a first upstream part (P1) and a second downstream part (P2) so as to establish a revised flight phase (PR).